Deployable structure
A deployable structure having a plurality of panel elements is provided. Adjacent panel elements are connected to one another by hinges. The hinges allow the panel elements to be placed in a stowed or folded configuration, in which adjacent pairs of panel elements are folded against one another to provide a relatively compact assembly. Biasing members can be provided to transition the deployable structure from the stowed configuration to a deployed configuration. When in the deployed configuration, the relative positions of the panel elements of the deployable structure are maintained, at least in part, by locating interface assemblies. The deployable structure may have a generally annular configuration when deployed.
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This application claims the benefit of U.S. Provisional Patent Application Ser. No. 61/922,539, filed Dec. 31, 2013, the entire disclosure of which is hereby incorporated herein by reference.
STATEMENT REGARDING FEDERALLY SPONSORED RESEARCH OR DEVELOPMENTThis invention was made with Government support under agreement number HR 0011-10-C-0157 awarded by DARPA. The Government has certain rights in the invention.
FIELDMethods and systems related to a space-based deployable structure are provided.
BACKGROUNDIt is often desirable to deploy relatively large structures in space. For example, telescopes, antennas, and other instruments can benefit from including large optical elements. However, such structures must fit within the relatively restricted cargo volume of a launch vehicle.
In order to provide relatively large elements as part of space-based instruments, techniques and structures have been developed that allow such elements to be carried in the launch vehicle in a folded or otherwise compact form. The element is then unfolded or otherwise deployed after that element has been removed from the launch vehicle. With respect to such techniques and structures, it is important to provide an element that can be deployed reliably, and with high precision.
Deployable structures, such as the primary element of telescopes, have been developed that unfold like a Chinese fan. Other systems have been proposed that unfold linearly. Still other proposed designs utilize an origami or umbrella type structure. However, such designs can suffer from relatively imprecise forms and insufficient stability in a deployed state, and insufficient reliability with respect to successful deployment of the structure.
SUMMARYIn accordance with at least some embodiments, a deployable structure has a folded configuration that is relatively compact, for transport to a deployment location. For example, in the folded configuration, the deployable structure can be dimensioned to fit within a standard evolved expendable launch vehicle (EELV) fairing. In a deployed configuration, the deployable structure may comprise an annular structure. In at least some embodiments, the deployable structure is the primary element of a space-based telescope. More particularly, the deployable structure may provide a diffractive optical element. In other embodiments, the deployable structure may provide a refractive or reflective optical element. In accordance with still other embodiments, the deployable structure discussed herein can be utilized to provide a relatively compact structure that can be deployed into a relatively large planar structure with high reliability.
The deployable structure includes a number of rigid panel elements or petals. In accordance with embodiments of the present disclosure, any even number of rigid panel elements can be provided. Each of the rigid panel elements is joined to two adjacent rigid panel elements. In particular, at least one hinge interconnects an adjacent pair of panel elements to one another. The hinges allow adjacent panel elements to fold relative to one another in alternating directions to form folded pairs of panel elements when the deployable structure is in the folded configuration.
In the folded configuration, a first hinge interconnecting a first panel element to a second panel element adjacent the first panel element on a first side of the first panel element allows the second panel element to fold in a first direction relative to a plane of the first panel element. A second hinge interconnecting the first panel element to a third panel element adjacent the first panel element on a second side of the first panel element allows the third panel element to fold in a second direction relative to the plane of the first panel element. In accordance with embodiments of the present disclosure, there are at least three folded pairs of panel elements when the deployable structure is in the folded configuration. Accordingly, the deployable structure includes at least six panel elements. In accordance with at least some embodiments of the present disclosure, the number of panel elements is an even number of six or greater. In accordance with further embodiments, the number of pairs of panel elements is evenly divisible by three.
The hinges allow the panel elements to transition from the stowed configuration, in which pairs of panel elements are folded against one another, to the deployed configuration. Biasing members can be incorporated into the hinges and/or can be separately provided to transition the deployable structure to the deployed configuration when the deployable structure is released from the folded configuration. In the deployed configuration, the deployable structure may have an annular form. In addition, locating assemblies maintain the relative position of panel elements when the deployable structure is in the deployed configuration.
In plan view the shape of the individual panel elements can be trapezoidal or approximately trapezoidal. Accordingly, each panel element can have a relatively short side that faces a center point of the annular deployed structure and a relatively long side opposite the short side that defines a portion of the outer circumference of the annular deployed structure. The sides of each panel element are not parallel to another, and each side is joined by a hinge to a side of an adjacent panel element.
Each of the panel elements can include a perimeter frame with first and second side members, an inner end member, and an outer end member. The perimeter frame can function to support one or more optical elements, directly or in connection with a sled assembly or other support structure.
Additional features and advantages of embodiments of the present disclosure will become more readily apparent from the following description, particularly when taken together with the accompanying drawings.
The folded structure 106 occupies a volume that generally has the form of a truncated cone. Moreover, in the stowed configuration, the deployable structure 104 features pairs 116 of panel elements 108 that lie in parallel or nearly parallel (i.e., at an angle of less than 10° with respect to one another). In addition, the folded pairs 116 of panel elements 108 can be arranged such that they are symmetric about radius lines that are evenly spaced about a center point of the folded structure 106. As discussed in greater detail elsewhere herein, the deployable structure 104 can include biasing elements that provide the energy necessary to reliably move the deployable structure 104 from the stowed configuration to the deployed configuration. Accordingly, in order to maintain the deployable structure 104 in the stowed configuration, retention straps or bands 118 (see
The deployed structure 107 can have a generally annular form in plan view. Accordingly, the sides of all the panel elements 108 and the hinges 112 generally lie along radii of the deployed structure 107. In addition, the deployable structure 104 is relatively planar in the deployed configuration, at least as compared to the stowed configuration. In accordance with still other embodiments, the deployed structure 107 may approximate a concave surface when viewed from a first side, and may approximate a convex surface when viewed from a second side opposite the first side.
In addition, the panel elements 108 can include a sled assembly 424 that is supported by the perimeter frame 404 (see also
A locating interface assembly 804 is depicted in
In accordance with embodiments of the present disclosure, the deployable structure 104 may be biased towards the deployed configuration by a spring or other biasing member 704. Accordingly, the deployable structure 104 may be configured to automatically transition itself to the deployed configuration when the deployable structure 104 is released from a launch vehicle or launch vehicle component. The energy required to transition deployable structure 104 to the deployed configuration can be provided by springs or other biasing members 704, for example that are incorporated into the hinges 112. The biasing members 704 can continue to provide a biasing force that, in combination with the locating members or interfaces 804, maintains the deployable structure 104 in the deployed configuration. Moreover, the deployed configuration can be maintained with high precision by the biasing members 704, the hinges 112, and the cooperating locating members 804. Alternatively or in addition, locating members 804 can be provided that lock the deployable structure 104 in the deployed configuration. The disclosed folded configuration, with at least three folded pairs of panel elements 108, in combination with the biasing force and at least three locating members 804 between adjacent panel elements 108, allows the deployable structure 104 to be deployed and maintained in the deployed configuration with high reliability.
With reference now to
At step 1016, pairs 116 of panel elements 108 are folded flat, against the biasing force, such that the first surfaces 120 of the panel elements 108 within each pair 116 face one another. In accordance with at least some embodiments, the panel elements 104 within each pair 116 can be folded so that the first surfaces 120 are in parallel planes. In accordance with other embodiments, the panel elements 108 may be folded so that the first surfaces 120 are within nearly parallel planes (e.g., within about 10° of one another). As can be appreciated by one of skill in the art after consideration of the present disclosure, folding the panel elements 108 within each pair 116 against one another will have the effect of drawing up the deployable structure 104, such that the maximum diameter of the deployable structure 104 is reduced as compared to the maximum diameter in the deployed configuration. Moreover, folding the deployable structure 104 will result in panel elements 108 in adjacent pairs 116 being folded towards one another. Thus folded, the deployable structure 104 is in a stowed configuration (i.e. is in the form of the folded structure 106). In accordance with embodiments of the present disclosure, the second surfaces 124 of adjacent panel elements 108 of adjacent pairs 116 lie in planes that intersect one another at a first angle, where the first angle is greater than zero. In accordance with still further embodiments, the angle of intersection of planes corresponding to the second surfaces 124 of adjacent panel elements 108 of adjacent pairs 116 is 10° or greater. Thus configured, the deployable structure 104 is secured in the stowed configuration by one or more bands or restraints 118 (step 1020).
The folded structure 106 can then be placed into the vehicle that will be used to transport the deployable structure 104 to a desired location (step 1024). For example, the deployable structure 104 may be placed within the fairing of a launch or other transport vehicle. The deployable structure 104, in the stowed configuration, can then be transported to the desired location (step 1028).
After the deployable structure 104 has been brought to the desired location, the deployable structure 104 can be removed from the vehicle (step 1032). The restraints 118 can then be released, allowing the biasing member 704 to place the deployable structure 104 in the deployed configuration (step 1036). In the deployed configuration, the locating interface assemblies 804 in cooperation with the biasing members 704, maintain adjacent panel elements 108 in a desired location relative to one another. The deployable structure 104 is then operational, and thus the telescope or other assembly or instrument of which the deployable structure 104 is a part can be operated (step 1040).
In an exemplary embodiment, the deployable structure 104 comprises a diffractive primary optical element of a space-deployed telescope. However, embodiments of the present disclosure are not so limited. In particular, a deployable structure 104 can be used to provide a precisely configured, planar or nearly planar component that can be transported to a deployment location in a relatively compact, folded configuration, and that can be deployed with high reliability, using a self-powered mechanism.
The foregoing discussion of the invention has been presented for purposes of illustration and description. Further, the description is not intended to limit the invention to the form disclosed herein. Consequently, variations and modifications commensurate with the above teachings, within the skill or knowledge of the relevant art, are within the scope of the present invention. The embodiments described hereinabove are further intended to explain the best mode presently known of practicing the invention and to enable others skilled in the art to utilize the invention in such or in other embodiments and with various modifications required by the particular application or use of the invention. It is intended that the appended claims be construed to include alternative embodiments to the extent permitted by the prior art.
Claims
1. A deployable structure, comprising:
- a plurality of panel elements, wherein each of the panel elements includes a perimeter having a first side edge and a second side edge, wherein the first side edge of a first panel element is not parallel to the second side edge of the first panel element, and wherein a total number of panel elements included in the plurality of panel elements is an even number; and
- a plurality of hinges, wherein at least a first hinge interconnects adjacent panel elements within a pair of panel elements of the plurality of panel elements to one another such that first surfaces of the panel elements within the pair can be folded towards one another, and wherein at least a second hinge interconnects adjacent panel elements in adjacent pairs of panel elements to one another such that second surfaces of the panel elements in the adjacent pairs can be folded towards one another; and
- a plurality of biasing members, wherein the biasing members bias the deployable structure towards a deployed configuration, and wherein the deployed configuration is planar.
2. The deployable structure of claim 1, wherein a number of pairs of panel elements included in the deployable structure is equal to a multiple of three.
3. The deployable structure of claim 1, wherein the biasing members are springs, and wherein at least some of the hinges are pivoting mechanisms.
4. The deployable structure of claim 1, wherein the deployed configuration of the deployable structure is approximately annular.
5. The deployable structure of claim 1, further comprising:
- a plurality of locating interface assemblies, wherein at least three locating interfaces are located between adjacent panel elements.
6. A deployable structure, comprising:
- a plurality of panel elements, wherein each of the panel elements includes a perimeter having a first side edge and a second side edge, wherein the first side edge of a first panel element is not parallel to the second side edge of the first panel element, and wherein a total number of panel elements included in the plurality of panel elements is an even number; and
- a plurality of hinges, wherein at least a first hinge interconnects adjacent panel elements within a pair of panel elements of the plurality of panel elements to one another such that first surfaces of the panel elements within the pair can be folded towards one another, and wherein at least a second hinge interconnects adjacent panel elements in adjacent pairs of panel elements to one another such that second surfaces of the panel elements in the adjacent pairs can be folded towards one another;
- a plurality of biasing members, wherein the biasing members bias the deployable structure towards a deployed configuration; and
- a plurality of locating interface assemblies, wherein at least three locating interfaces are located between adjacent panel elements, each locating interface including at least one of: a protruding member; and a receiving member.
7. The deployable structure of claim 6, wherein a protruding member of a first locating interface assembly associated with a first panel element and a receiving member of a second locating interface assembly associated with a second panel element are in contact with one another when the deployable structure is in the deployed configuration.
8. A deployable structure, comprising:
- a plurality of panel elements, wherein each of the panel elements includes a perimeter having a first side edge and a second side edge, wherein the first side edge of a first panel element is not parallel to the second side edge of the first panel element, and wherein a total number of panel elements included in the plurality of panel elements is an even number; and
- a plurality of hinges, wherein at least a first hinge interconnects adjacent panel elements within a pair of panel elements of the plurality of panel elements to one another such that first surfaces of the panel elements within the pair can be folded towards one another, wherein at least a second hinge interconnects adjacent panel elements in adjacent pairs of panel elements to one another such that second surfaces of the panel elements in the adjacent pairs can be folded towards one another, wherein each of the panel elements includes at least one optical element, and wherein the at least one optical element is a transmissive diffractive optical element.
9. The deployable structure of claim 8, wherein the deployable structure is a primary optical element of a space-deployed telescope.
10. A deployable structure, comprising:
- a plurality of panel elements, wherein each panel element in the plurality of panel elements includes first and second side edges, an inner edge, an outer edge, and first and second surfaces, wherein each of the panel elements is planar, and wherein the plurality of panel elements includes an even number of panel elements;
- a plurality of hinges, wherein the first side edge of each panel element is interconnected by at least one of the hinges to the second side edge of an adjacent panel element, wherein for each of the panel elements the at least one hinge on the first side edge allows the adjacent panel element to pivot towards first surface of the panel element, and wherein for each of the panel elements the at least one hinge on the second side edge allows the other adjacent panel element to pivot towards the second surface of the panel element.
11. The deployable structure of claim 10, wherein a deployed configuration of the deployable structure is approximately annular.
12. The deployable structure of claim 10, wherein the deployable structure is movable from a stowed configuration to a deployed configuration.
13. The deployable structure of claim 12, further comprising:
- a plurality of biasing members, wherein the deployable structure is biased towards the deployed configuration by the biasing members.
14. The deployable structure of claim 13, wherein the deployable structure has a form of a truncated cone in the stowed configuration, wherein the deployable structure has an annular form in the deployed configuration, and wherein each of the hinges is located along a radius of the truncated cone with the deployable structure in the stowed configuration and along a radius of the annular form in the deployed configuration.
15. A method for providing a deployable structure, comprising:
- joining side edges of a plurality of panel elements to one another by hinges, wherein each panel element includes a first side edge, a second side edge, an inner edge, and an outer edge, wherein the first side edge of each panel element is interconnected to the second side edge of an adjacent panel element by at least one of the hinges;
- biasing the panel elements towards a deployed configuration in which the deployable structure has an annular form, and in which the hinges lie along radii of the deployable structure in the deployed configuration, wherein the inner side edges of each of the panel elements define an aperture of the annular form, and wherein the outer side edges of each of the panel elements forms an outer perimeter of the annular form.
16. The method of claim 15, further comprising:
- folding the panel elements in pairs, such that a first surface of each panel element faces a first surface of a paired panel element, and such that a second surface of each panel element faces a second surface of a panel element in an adjacent pair of panel elements, whereby the deployable structure is placed in a stowed configuration;
- securing the deployable structure in the stowed configuration.
17. The method of claim 16, further comprising:
- transporting the deployable structure to a deployment location while the deployable structure is in the stowed configuration.
18. The method of claim 17, further comprising:
- releasing the deployable structure from the stowed configuration, wherein the panel elements are allowed to move into the deployed configuration.
19. The method of claim 16, wherein in the stored configuration the deployable structure has a form of a truncated cone.
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Type: Grant
Filed: Dec 31, 2014
Date of Patent: Jul 18, 2017
Assignee: Ball Aerospace & Technologies Corp. (Boulder, CO)
Inventors: Aaron J. Seltzer (Boulder, CO), David M Waller (Westminster, CO), Lawrence J. Campbell (Westminster, CO), Ryan T. Thompson (Longmont, CO), Dustin S. Putnam (Broomfield, CO), William D. Tandy (Boulder, CO)
Primary Examiner: Frank Font
Application Number: 14/587,342
International Classification: G02B 23/20 (20060101); G02B 27/42 (20060101); G02B 5/18 (20060101);